马赫数10超燃冲压发动机激波风洞实验研究

Experimental Study on a Scramjet at Mach 10 in Shock Tunnel

关键词:  超燃冲压发动机  超声速燃烧  激波风洞  自由射流  试验

Key words:  Scramjet  Supersonic combustion  Shock tunnel  Free jet  Test

摘要:

基于室温氢气驱动激波风洞实现总压28MPa，总焓4.7MJ/kg，名义马赫数10超声速空气自由来流模拟，开展二维超燃冲压发动机自由射流点火实验，实现稳定燃烧，燃烧持续时间5ms。通过此次试验，探索尝试了马赫数10超燃冲压发动机地面点火燃烧试验技术，初步获得了高马赫数超燃冲压发动机点火/燃烧过程参数和基本现象规律。试验中，采用高速相机完整记录了氢气喷注、着火、燃烧现象和燃烧持续过程，采用高频压力传感器和热电偶进行沿程壁面压力和热流测量。研究结果表明，马赫数10自由来流条件下，气态氢燃料垂直喷入超声速来流能够实现自点火，并发生剧烈燃烧，燃烧区域压力上升幅度40%，壁面热流上升幅度达100%。

Abstract:

Based on the shock tunnel driven by the room temperature hydrogen， nominal Mach number 10 hypersonic air free stream with total pressure of 28MPa， total enthalpy of 4.7MJ/kg can be achieved. Experiments of the free jet ignition performance of a 2-dimensional scramjet were conducted in the shock tunnel. The results revealed that stable combustion can last about 5ms. Through this experiment， the ground test techniques of the Ma 10 scramjet were explored， the scramjet ignition/combustion processes and the basic phenomenon were obtained. During the testing， the hydrogen injection， ignition， combustion phenomenon and continuous combustion process were completely recorded by a high-speed camera， and the wall pressure and wall heat flux were measured by high-frequency pressure sensors and thermocouples respectively. The results show that under the condition of Mach number 10 air free stream， the gaseous hydrogen injected into the supersonic flow vertically is able to achieve ignition and intense combustion， the pressure in the combustion region increases by 40%， and the wall heat flux increases by 100%.